Gliding parachute

Abstract

A gliding parachute of the flexible, multi-cell airfoil type having a length to width ratio in the range of approximately 2:1 to 2.85:1, a maximum camber height to chord ratio in the range of approximately 0.1:1 to 0.2:1, a wing span to load attachment distance ratio of approximately 2:1, and an attachment point approximately 25% to 45% of the chord aft of the leading edge. The suspension lines and the fabric sections of the wing are dimensioned to impart a side to side curvature to the inflated wing. The gliding parachute has superior maneuverability and lift. A special pilot chute and bridle assembly are provided so that upon deployment of the main chute the pilot chute will automatically collapse to substantially reduce its drag, thereby improving the glide ratio of the main parachute.

I claim: 
     
       1. A flexible and inflatable gliding wing comprising aligned upper and lower flexible panels each having a generally rectangular configuration and a length to width ratio in the range of approximately 2:1 to approximately 2.85:1, the panels being connected to one another by a plurality of vertically extending airfoil-shaped ribs extending transversely across the panels at longitudinally spaced locations to define a plurality of cells so that upon inflation of the wing one adjacent set of the longitudinal edges of the panels will be vertically spaced apart to form the leading edge of the wing to permit air to flow rearwardly through the cells, the portion of the upper panel defining the upper wall of each cell having a greater longitudinal dimension than the portion of the lower panel defining the lower wall of the cell, the ribs including side ribs and a center rib between each adjacent pair of side ribs, the center ribs having greater camber height than the side ribs, the ratio of the maximum camber height of the ribs to the chord thereof being in the range of approximately 0.1:1 to approximately 0.2:1, a pair of generally triangular flexible stabilizers each having its base edge secured to, and extending downwardly from one of the side edges of the lower panel, and each stabilizer having an apex positioned at least 50% of the chord aft of the leading edge of the wing, and a plurality of suspension lines connected to the wing and extending downward from the wing in converging relationship to at least one point of attachment for a load, the upper ends of the suspension lines being connected to the ribs to define a plurality of longitudinally spaced and transversely extending rows of suspension lines, the suspension lines being proportioned in length so that during flight the suspension lines impart a longitudinal arcuate curvature to the wing, the ratio of the span of the wing to the vertical distance between the attachment point and the lower panel is approximately 2:1, and the attachment point is in the range of approximately 25% to approximately 45% of the chord aft of the leading edge of the wing. 
     
     
       2. The invention of claim 1 wherein: the upper panel is connected to the upper edge of each of the ribs; and   the shape of the upper edge of each of the ribs includes a convexly curved forward portion, and first, second and third straight segments tapering downwardly to the trailing edge of the wing, the first segment being connected to the curved portion, the second segment extending at an angle of approximately 3 degrees downwardly from the first segment, and the third segment extending at angle of approximately 3 degrees downwardly from the second segment.   
     
     
       3. The invention of claim 1 wherein: the upper panel is connected to the upper edge of each of the ribs;   the shape of the upper edge of each of the ribs includes a convexly curved forward portion, a convexly curved intermediate portion tapering downwardly toward the trailing edge of the wing; and a concavely curved rearward portion tapering downwardly to the trailing edge of the wing; and   the shape of the lower edge of each of the ribs includes a concavely curved forward portion and a convexly curved rearward portion.   
     
     
       4. In combination: a flexible and inflatable gliding wing parachute having a large canopy and a plurality of load suspension lines which extend therefrom;   a pilot chute having a small canopy and a plurality of suspension tapes which extend therefrom; and   means for connecting the pilot chute to the gliding wing parachute including a bridle attachment line extending across the medial portion of the large canopy and secured at its opposite ends to corresponding ones of the suspension lines, a deployment bag for enclosing the large canopy, an outer bridle having an upper end connected to the suspension tapes and a lower end connected to the deployment bag, a handle located on top of the small canopy, and a central bridle line slidable within the outer bridle, the central bridle line having an upper end which extends through the center of the small canopy and is secured to the handle and a lower end which extends through the deployment bag and is connected to the bridle attachment line,   whereby during descent with the large canopy packed in the deployment bag, and the suspension lines, pilot chute and connecting means folded adjacent the deployment bag, pulling on the handle will cause the pilot chute to inflate, extend the outer bridle and central bridle line to cause the suspension lines to unfold, thereafter pull the deployment bag away from the large canopy, and thereafter permit the large canopy to inflate to pull the central bridle line downwardly through the outer bridle, thereby causing the handle to collapse the small canopy and substantially reduce the drag of the pilot chute.